High-precision positioning and damping clamping tool for main speed reducer shell of helicopter

Abstract

The application relates to the technical field of helicopter part machining, and discloses a high-precision positioning and damping clamping tool for a helicopter main speed reducer shell, which comprises an operation table, a machining table is fixedly connected to the operation table, an adjusting assembly is arranged on the machining table, the adjusting assembly is used for synchronously driving a first limiting assembly and a second limiting assembly to adjust positions, a guide assembly is fixedly connected to the upper surface of the machining table, the guide assembly is used for guiding and limiting the movement process of the first limiting assembly and the second limiting assembly, the second limiting assembly comprises a cylinder, a second limiting plate and a second rubber pad, the output end of the cylinder is connected with the second limiting plate, and a contact type vibration sensor is arranged on the inner surface of the second limiting plate. Without increasing an excessively large initial clamping force, the closed-loop active damping structure is constructed, workpiece deflection and thin-wall deformation are prevented, and the positioning precision and machining stability are improved.

Description

Technical Field

[0001] This invention relates to the field of helicopter component processing technology, specifically a high-precision positioning and vibration damping clamping fixture for the main gearbox housing of a helicopter. Background Technology

[0002] The helicopter main gearbox is an important component of the helicopter transmission system. Its housing is usually used to install, support and protect internal transmission components such as gears, shafts and bearings. Because the helicopter main gearbox housing is usually characterized by large structural size, irregular shape, large wall thickness difference and complex positioning reference, special clamping fixtures are required to position and fix the housing workpiece when it is machined by milling, drilling and boring. This is to ensure the positional accuracy between the machining references during the machining process and reduce the impact of workpiece displacement or vibration on the machining quality.

[0003] Existing methods for machining and clamping helicopter main gearbox housings typically involve placing the housing component on a machining table or positioning base. Pre-set positioning holes on the housing component, along with positioning pins, positioning columns, or other positioning structures, are used to determine the position of the housing component relative to the machining equipment. The housing component is then fixed in place by pressure plates, clamping blocks, or other clamping mechanisms. During machining, the engagement between the positioning holes and positioning structures primarily restricts the movement of the component in a specific direction. The clamping mechanism applies a clamping force to the component, keeping it in the predetermined machining position, thus completing subsequent machining.

[0004] Currently, when helicopter main gearbox housing parts are positioned solely by locating holes and locating structures, positional constraints can only be formed in a limited direction. It is difficult to form multi-directional and multi-position coordinated constraints for the inner and outer regions of the housing parts. When subjected to cutting forces, impact loads, and periodic vibrations, the parts may exhibit local sway, slight displacement, or vibration amplification. At the same time, the clamping positions and clamping strokes of existing clamping structures are usually relatively fixed, which is insufficient to adapt to housing parts with different wall thicknesses, different local heights, or different structural dimensions, requiring repeated manual adjustments to the clamping positions. Furthermore, most existing clamping fixtures use preset clamping forces for static clamping, making it difficult to dynamically adjust the clamping force according to the actual vibration state of the parts during processing. Insufficient initial clamping force can easily affect processing stability, while excessive clamping force may cause local deformation in thin-walled areas.

[0005] Therefore, the purpose of this invention is to provide a high-precision positioning and vibration damping clamping fixture for the helicopter main gearbox housing, so as to overcome the shortcomings of the prior art. Summary of the Invention

[0006] To address the shortcomings of existing technologies, this invention provides a high-precision positioning and vibration-damping clamping fixture for helicopter main gearbox housings. This fixture solves the problems of poor workpiece positioning adaptability caused by single spatial limitation and fixed clamping stroke during the machining and clamping of existing helicopter main gearbox housings, as well as the inability to dynamically adjust the clamping force according to machining vibrations when using static clamping, which easily leads to workpiece sway, micro-displacement, or local deformation of thin walls.

[0007] To achieve the above objectives, the present invention provides the following technical solution: A high-precision positioning and vibration damping clamping fixture for a helicopter main gearbox housing includes an operating table, a processing table fixedly connected to the operating table, and an adjustment component provided on the processing table. The adjustment component is used to synchronously drive a first limit component and a second limit component to adjust their positions. A guide assembly is fixedly connected to the upper surface of the processing table. The guide assembly is used to guide and limit the movement of the first limiting assembly and the second limiting assembly. The second limiting component includes a cylinder, a second limiting plate, and a second rubber pad. The output end of the cylinder is connected to the second limiting plate. A contact vibration sensor is provided on the inner surface of the second limiting plate. The second rubber pad is located on the side of the second limiting plate close to the workpiece to be clamped. The upper surface of the operating table is provided with a positioning platform, which is used to position and place the helicopter main gearbox housing to be processed. A controller is fixedly connected to the upper surface of the operating table. The contact vibration sensor is electrically connected to the controller, and the controller is electrically connected to the cylinder.

[0008] Preferably, the adjustment component includes a drive motor, the processing table has a placement cavity inside, the top inner wall of the placement cavity is fixedly connected to the drive motor, the output end of the drive motor is fixedly connected to a rotating disk through a rotating shaft, the rotating disk has a first guide groove inside, and a guide post is provided inside the first guide groove.

[0009] Preferably, a movable platform is fixedly connected to the upper surface of the guide post, and the upper surface of the movable platform is fixedly connected to the first limiting component and the second limiting component respectively.

[0010] Preferably, the first limiting component includes a first fixing block, the lower surface of the first fixing block is fixedly connected to the moving platform, and the side surface of the first fixing block is fixedly connected to a first rubber pad through a first limiting plate.

[0011] Preferably, the second limiting component further includes a second fixing block, the upper surface of the moving platform is fixedly connected to the second fixing block, the side surface of the second fixing block is fixedly connected to the cylinder, the inner surface of the second rubber pad is fixedly connected to the contact vibration sensor, and the inner surface of the second limiting plate is fixedly connected to the second rubber pad.

[0012] Preferably, a fixing frame is fixedly connected to the upper surface of the operating table, and the upper surface of the fixing frame is fixedly connected to the positioning table.

[0013] Preferably, there are multiple first guide grooves, guide posts, moving platforms, first limiting components, and second limiting components, which are arranged in a circular array.

[0014] Preferably, the guide assembly includes a slider, the upper surface of which is fixedly connected to the moving platform, and a second guide groove is provided inside the slider.

[0015] Preferably, a guide block is fixedly connected to the upper surface of the processing table, and the inner surface of the second guide groove is slidably connected to the guide block.

[0016] Preferably, the controller has a preset vibration threshold. During the processing, the contact vibration sensor is used to collect the vibration signal of the helicopter main gearbox housing in real time and transmit it to the controller. When the controller determines that the received vibration parameter exceeds the preset vibration threshold, the controller controls the cylinder to perform dynamic stroke compensation in order to dynamically adjust the clamping force on the helicopter main gearbox housing.

[0017] This invention provides a high-precision positioning and vibration damping clamping fixture for the housing of a helicopter main gearbox. It has the following advantages: 1. This invention, by setting up an adjustment component, a first limiting component, a second limiting component, and a positioning platform, enables the helicopter main gearbox housing to be initially positioned. After placement, the first limiting component limits the reference position inside the housing, and the second limiting component assists in clamping different positions outside the housing. This allows for coordinated internal and external, multi-point distribution, and multi-directional constraint of the workpiece. Simultaneously, the adjustment component can drive the corresponding limiting structure to adjust its position, allowing each limiting point to quickly approach the predetermined clamping position according to the actual contour of the workpiece. This improves clamping efficiency while constructing a more stable spatial constraint structure, reducing the possibility of the workpiece shifting, swaying, or loosening under cutting loads. This improves the positioning accuracy and clamping stability during the machining process of the helicopter main gearbox housing.

[0018] 2. By setting an adjustable second limiting component, the present invention can adaptively adjust the stroke according to the thickness and shape of different areas of the workpiece, thereby improving the adaptability of the clamping fixture to workpieces of different thicknesses and sizes. It can also reduce the situation where the rigid clamping structure directly acts on the shell surface, resulting in indentations or local stress concentration, so that the clamping fixture has both rigid positioning and flexible vibration reduction functions.

[0019] 3. This invention constructs a closed-loop active stabilizing clamping structure based on the vibration state feedback of the workpiece by setting a contact vibration sensor, a controller, and a second limit component that can dynamically adjust the clamping state. During the processing, the vibration information of the helicopter main reducer housing workpiece is collected in real time. The controller calculates and judges based on the detected vibration parameters, and can compensate for abnormal vibrations or clamping slack trends that occur during the processing in a timely manner without excessively increasing the initial clamping force. This reduces the possibility of micro-displacement of the workpiece caused by continuous vibration, while avoiding the use of a large clamping force all the time, which would cause local deformation of the housing. Thus, it takes into account the processing stability, positioning accuracy, and housing structure protection effect. Attached Figure Description

[0020] Figure 1 This is a schematic diagram of the overall structure of the present invention; Figure 2 This is a front view of the present invention; Figure 3 This is a top view of the present invention; Figure 4 This is an exploded view of the processing table of the present invention; Figure 5 This is a schematic diagram of the internal structure of the processing table of the present invention; Figure 6 This is a schematic diagram of the second limiting component structure of the present invention.

[0021] The components include: 1. Operating table; 2. Processing table; 3. Adjustment assembly; 301. Drive motor; 302. Rotary disk; 303. First guide groove; 304. Guide column; 305. Moving table; 4. Placement cavity; 5. First limiting assembly; 501. First fixing block; 502. First limiting plate; 503. First rubber pad; 6. Second limiting assembly; 601. Second fixing block; 602. Cylinder; 603. Second limiting plate; 604. Second rubber pad; 7. Guide assembly; 701. Guide block; 702. Slider; 703. Second guide groove; 8. Fixing frame; 9. Positioning table; 10. Processed part of helicopter main reducer housing; 11. Controller; 12. Contact vibration sensor. Detailed Implementation

[0022] The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0023] Please see the appendix Figure 1 - Appendix Figure 4 This invention provides a high-precision positioning and vibration damping clamping fixture for a helicopter main gearbox housing, including an operating table 1, a processing table 2 fixedly connected to the operating table 1, an adjustment component 3 provided on the processing table 2, the adjustment component 3 being used to synchronously drive a first limiting component 5 and a second limiting component 6 to adjust their positions, the adjustment component 3 including a drive motor 301, a placement cavity 4 opened inside the processing table 2, the top inner wall of the placement cavity 4 being fixedly connected to the drive motor 301, the output end of the drive motor 301 being fixedly connected to a rotating disk 302 via a rotating shaft, a first guide groove 303 opened inside the rotating disk 302, a guide post 304 provided inside the first guide groove 303, a moving platform 305 fixedly connected to the upper surface of the guide post 304, and the upper surface of the moving platform 305 being fixedly connected to the first limiting component 5 and the second limiting component 6 respectively.

[0024] Specifically, the adjustment component 3 precisely converts the rotational motion of the drive motor 301 into the linear translational motion of the moving stage 305. In the initial clamping stage, the drive motor 301, located within the placement cavity 4, is activated. The output of the drive motor 301 drives the rotating disk 302 to rotate at a constant speed. Since the first guide groove 303 is located inside the rotating disk 302 and has a specific eccentric groove, when the rotating disk 302 rotates, the inner wall of the first guide groove 303 continuously agitates the guide post 304, forcing the guide post 304 to cause directional displacement of the moving stage 305 fixed on its upper surface. This allows the first limiting component 5 and the second limiting component 6 on the moving stage 305 to quickly and synchronously approach the predetermined clamping position according to the actual contour of the helicopter main gearbox housing part 10. The adjustment component 3 improves clamping efficiency and simultaneously quickly constructs a more stable and efficient spatial constraint limiting structure around the helicopter main gearbox housing part 10.

[0025] Please see the appendix Figure 4 - Appendix Figure 6A guide component 7 is fixedly connected to the upper surface of the processing table 2. The guide component 7 is used to guide and limit the movement of the first limiting component 5 and the second limiting component 6. The first limiting component 5 includes a first fixing block 501. The lower surface of the first fixing block 501 is fixedly connected to the moving table 305. The side surface of the first fixing block 501 is fixedly connected to a first rubber pad 503 through a first limiting plate 502. Multiple first guide grooves 303, guide posts 304, moving table 305, first limiting component 5 and second limiting component 6 are provided and are distributed in a ring array.

[0026] Specifically, the guide component 7 provides strict linear trajectory constraints for the smooth movement of the first limiting component 5 and the second limiting component 6, preventing the multiple sets of first limiting components 5 and second limiting components 6 from swaying when moving or being clamped. When the moving table 305 moves toward the helicopter main gearbox housing part 10, the multiple first limiting components 5 arranged in a ring array first enter the limiting position. The first fixing block 501 transmits the thrust to the first rubber pad 503 through the first limiting plate 502, so that the first rubber pad 503 fits tightly against and presses against the inner reference position of the helicopter main gearbox housing part 10.

[0027] The multi-point distributed ring array layout realizes multi-directional coordinated positioning of the internal area of ​​the helicopter main gearbox housing 10, preventing the workpiece from local swaying when subjected to rotary cutting force; at the same time, the first rubber pad 503, as a flexible contact medium, avoids the mechanical indentation or stress concentration caused by the rigid metal structure directly squeezing the inner wall of the housing, and plays a basic role in flexible support and positioning.

[0028] Please see the appendix Figure 6 The second limiting component 6 includes a cylinder 602, a second limiting plate 603, and a second rubber pad 604. The output end of the cylinder 602 is connected to the second limiting plate 603. A contact vibration sensor 12 is provided on the inner surface of the second limiting plate 603. The second rubber pad 604 is located on the side of the second limiting plate 603 near the workpiece to be clamped. The second limiting component 6 also includes a second fixing block 601. The upper surface of the moving stage 305 is fixedly connected to the second fixing block 601. The side surface of the second fixing block 601 is fixedly connected to the cylinder 602. The inner surface of the second rubber pad 604 is fixedly connected to the contact vibration sensor 12. The inner surface of the second limiting plate 603 is fixedly connected to the second rubber pad 604.

[0029] Specifically, after the first limiting component 5 completes the inner positioning, the cylinder 602 fixed on the second fixing block 601 is started. The output end of the cylinder 602 pushes the second limiting plate 603 and the second rubber pad 604 to extend to different positions outside the housing. Since the helicopter main reducer housing has a large difference in wall thickness, the traditional fixed stroke clamp is difficult to fit. By setting the cylinder 602 as an adjustable flexible power source, the stroke can be adaptively adjusted according to the wall thickness of different areas of the helicopter main reducer housing machining part 10, ensuring that the second rubber pad 604 covers and fits the outside of the housing.

[0030] The second limiting component 6 works in conjunction with the first limiting component 5 to form a stable internal and external dual clamping structure. At the same time, the contact vibration sensor 12, which is wrapped inside the second rubber pad 604, can be tightly attached to the outer wall of the helicopter main gearbox housing machining part 10, providing accurate front-end data acquisition for subsequent real-time dynamic vibration reduction, so that the clamping fixture has both rigid positioning and flexible vibration reduction performance.

[0031] Please see the appendix Figure 4 The guide assembly 7 includes a slider 702, the upper surface of which is fixedly connected to the moving stage 305. A second guide groove 703 is provided inside the slider 702. A guide block 701 is fixedly connected to the upper surface of the processing stage 2. The inner surface of the second guide groove 703 is slidably connected to the guide block 701.

[0032] Specifically, when the moving stage 305 is displaced by the adjustment component 3, the slider 702 fixed at the bottom of the moving stage 305 will move synchronously. Since the second guide groove 703 inside the slider 702 is in a tight sliding fit with the guide block 701 fixed on the processing table 2, the guide block 701 can withstand the shearing force and impact load from various sides brought about by the processing technology. The heavy-duty sliding guide setting of the second guide groove 703 and the guide block 701 reduces the possibility of slight displacement or vibration of the moving stage 305 and the first limit component 5 and the second limit component 6 under the action of cutting load, and ensures the positioning accuracy of the helicopter main reducer housing processing part 10 during the processing.

[0033] Please see the appendix Figure 4 A fixed frame 8 is fixedly connected to the upper surface of the operating table 1. The upper surface of the fixed frame 8 is fixedly connected to the positioning table 9. The positioning table 9 is provided on the upper surface of the operating table 1. The positioning table 9 is used to position and place the helicopter main reducer housing processing part 10 to be processed.

[0034] Specifically, the positioning platform 9, the fixing frame 8, and the operating platform 1 constitute the initial static reference bearing structure of the clamping fixture. Due to the large structural size and uneven weight distribution of the helicopter main reducer housing machining part 10, after the helicopter main reducer housing machining part 10 is placed, the inner surface of the helicopter main reducer housing machining part 10 fits against the positioning platform 9. The fixing frame 8 fixes the positioning platform 9 on the operating platform 1, ensuring the stability of the bottom reference surface installation. At the same time, the position setting of the fixing frame 8 will not affect the use of the adjustment component 3, the first limit component 5, and the second limit component 6.

[0035] Please see the appendix Figure 1 A controller 11 is fixedly connected to the upper surface of the operating table 1. A contact vibration sensor 12 is electrically connected to the controller 11. The controller 11 is electrically connected to the cylinder 602. The controller 11 has a preset vibration threshold. During the processing, the contact vibration sensor 12 is used to collect the vibration signal of the helicopter main gearbox housing 10 in real time and transmit it to the controller 11. When the controller 11 determines that the received vibration parameter exceeds the preset vibration threshold, the controller 11 controls the cylinder 602 to perform dynamic stroke compensation in order to dynamically adjust the clamping force on the helicopter main gearbox housing 10.

[0036] Specifically, during high-frequency machining of the helicopter main gearbox housing 10, the contact vibration sensor 12 acquires real-time vibration amplitude information of the local area of ​​the housing at a millisecond-level sampling frequency and converts it into an electrical signal, which is then transmitted to the controller 11. To avoid excessive initial clamping force causing deformation of the thin-walled housing or insufficient initial clamping force leading to machining loosening, the controller 11 incorporates a dynamic clamping force compensation algorithm. To achieve accurate compensation for abnormal vibrations, the controller 11 calculates the dynamic compensation output pressure of the cylinder 602 in real time based on the following formula: ; in, The target control pressure, dynamically adjusted, is output by controller 11 to cylinder 602, in MPa. The preset initial base pressure when cylinder 602 completes the initial clamping is indicated by MPa. This pressure value is relatively small and is designed to ensure that the helicopter main gearbox housing 10 does not undergo local deformation. This represents the comprehensive vibration amplitude parameter of the helicopter main gearbox housing 10, which is collected in real time by the contact vibration sensor 12 at the current moment, in mm / s. 2 or μm; This indicates the preset safety vibration threshold parameter within the controller 11. This threshold is the critical vibration value obtained in advance by establishing a finite element simulation analysis (FEA) model of the machined part 10 of the helicopter main gearbox housing, combined with the yield strength of the material and the boundary conditions of the allowable machining tolerance zone, or by conducting a preliminary actual cutting calibration test.

[0037] This represents the dynamic proportional compensation coefficient, used to control the steady-state gain of the vibration exceeding the limit on the pressure of cylinder 602. This is to ensure the smoothness of the cylinder 602's response and prevent overcompensation from causing system oscillation. The value range is from 0.1 to 0.5; The differential damping coefficient is used to determine the instantaneous rate of change of vibration amplitude over time. Provides feedforward compensation to suppress sudden impact loads. The preferred value range is 0.01 to 0.1. In actual processing and debugging, and The values ​​can be fine-tuned using conventional trial-and-error methods or critical proportional methods, based on the rigidity and cutting parameters of the machine tool on site.

[0038] Calculated using the above formula, when the processing is stable ( When the cylinder 602 applies only a small initial holding force, To protect the shell structure; once it cuts in, it may cause amplification of local vibrations or a tendency to loosen ( The controller 11 immediately increases the thrust of cylinder 602 instantaneously based on the ratio and rate of change, performing dynamic stroke compensation. This causes the second rubber pad 604 to apply stronger compression and vibration absorption, thereby reducing micro-displacement caused by continuous vibration without excessively increasing the initial rigid load. This balances the effects of processing stability, high-precision positioning, and thin-walled shell structure protection. The controller 11 is connected to the air circuit of cylinder 602 via an electro-proportional valve, used to precisely adjust the output force of cylinder 602 according to the calculated target control pressure.

[0039] Working principle: When using this device, the helicopter main gearbox housing part 10 to be processed is placed on the positioning table 9. The positioning table 9 is fixed on the operating table 1 by the fixing frame 8, which completes the initial basic support and positioning of the helicopter main gearbox housing part 10. The drive motor 301 is started. The output end of the drive motor 301 drives the rotating disk 302 to rotate. When the rotating disk 302 rotates, the first guide groove 303 inside the rotating disk 302 moves the guide column 304, thereby pushing the moving table 305 to move as a whole in the direction of the helicopter main gearbox housing part 10.

[0040] During the movement of the moving table 305, the slider 702 slides along the guide block 701 on the processing table 2 through the second guide groove 703. As the moving table 305 advances, multiple first limiting components 5 and second limiting components 6 arranged in a ring array simultaneously move closer to the helicopter main reducer housing processing part 10. The first rubber pad 503 at the end of the first limiting component 5 first presses against the inner reference position of the helicopter main reducer housing processing part 10 to form an internal basic constraint. After the first limiting component 5 completes the inner limiting, the cylinder 602 in the second limiting component 6 is activated. The cylinder 602 pushes the second limiting plate 603 and the second rubber pad 604 to extend to the outer surface of the helicopter main gearbox housing 10. Since the helicopter main gearbox housing has the characteristics of large wall thickness difference and irregular shape, each cylinder 602 can adaptively adjust its stroke according to the actual contour thickness of its facing area until the second rubber pad 604 is completely in contact with the outside of the housing. The first limiting component 5 and the second limiting component 6 achieve spatial three-dimensional clamping with internal and external coordination, multi-point distribution and multi-directional constraint. During the machining process, the contact vibration sensor 12, which is in close contact with the machined part 10 of the helicopter main gearbox housing, collects the vibration signals of each clamping point of the machined part 10 of the helicopter main gearbox housing in real time and converts them into electrical signals and transmits them to the controller 11. When the vibration parameters are within the preset threshold, the controller 11 maintains the current clamping force of the cylinder 602 unchanged to avoid deformation of the thin-walled area due to excessive initial clamping force. When the vibration parameters are detected to exceed the preset threshold, the controller 11 responds quickly and sends a command to the cylinder 602 in the corresponding area to control the cylinder 602 to perform dynamic stroke compensation, that is, to instantly increase the thrust of the cylinder 602, thereby actively absorbing and suppressing abnormal vibration. When the vibration falls back to within the safe threshold, the cylinder 602 can return to the normal clamping state.

Claims

1. A high-precision positioning and vibration damping clamping fixture for a helicopter main gearbox housing, comprising an operating table (1), wherein a processing table (2) is fixedly connected to the operating table (1), characterized in that, The processing table (2) is provided with an adjustment component (3), which is used to synchronously drive the first limit component (5) and the second limit component (6) to adjust their positions. The upper surface of the processing table (2) is fixedly connected to a guide component (7), which is used to guide and limit the movement of the first limiting component (5) and the second limiting component (6). The second limiting component (6) includes a cylinder (602), a second limiting plate (603) and a second rubber pad (604). The output end of the cylinder (602) is connected to the second limiting plate (603). A contact vibration sensor (12) is provided on the inner surface of the second limiting plate (603). The second rubber pad (604) is located on the side of the second limiting plate (603) close to the workpiece to be clamped. The inner surface of the second rubber pad (604) is fixedly connected to the contact vibration sensor (12). The inner surface of the second limiting plate (603) is fixedly connected to the second rubber pad (604). The upper surface of the operating table (1) is provided with a positioning table (9), which is used to position and place the helicopter main reducer housing part (10) to be processed. A controller (11) is fixedly connected to the upper surface of the operating table (1), the contact vibration sensor (12) is electrically connected to the controller (11), and the controller (11) is electrically connected to the cylinder (602). The controller (11) has a preset vibration threshold. During the processing, the contact vibration sensor (12) is used to collect the vibration signal of the helicopter main reducer housing part (10) in real time and transmit it to the controller (11). When the controller (11) determines that the received vibration parameter exceeds the preset vibration threshold, the controller (11) controls the cylinder (602) to perform dynamic stroke compensation in order to dynamically adjust the clamping force on the helicopter main reducer housing part (10).

2. The high-precision positioning and vibration damping clamping fixture for a helicopter main gearbox housing according to claim 1, characterized in that, The adjustment component (3) includes a drive motor (301). The processing table (2) has a placement cavity (4) inside. The top inner wall of the placement cavity (4) is fixedly connected to the drive motor (301). The output end of the drive motor (301) is fixedly connected to a rotating disk (302) through a rotating shaft. The rotating disk (302) has a first guide groove (303) inside. The first guide groove (303) has a guide post (304) inside.

3. The high-precision positioning and vibration damping clamping fixture for a helicopter main gearbox housing according to claim 2, characterized in that, The upper surface of the guide post (304) is fixedly connected to a movable stage (305), and the upper surface of the movable stage (305) is fixedly connected to the first limiting component (5) and the second limiting component (6) respectively.

4. The high-precision positioning and vibration damping clamping fixture for a helicopter main gearbox housing according to claim 3, characterized in that, The first limiting component (5) includes a first fixing block (501), the lower surface of the first fixing block (501) is fixedly connected to the moving platform (305), and the side surface of the first fixing block (501) is fixedly connected to a first rubber pad (503) through a first limiting plate (502).

5. The high-precision positioning and vibration damping clamping fixture for a helicopter main gearbox housing according to claim 3, characterized in that, The second limiting component (6) further includes a second fixing block (601), the upper surface of the moving stage (305) is fixedly connected to the second fixing block (601), and the side surface of the second fixing block (601) is fixedly connected to the cylinder (602).

6. The high-precision positioning and vibration damping clamping fixture for a helicopter main gearbox housing according to claim 1, characterized in that, The upper surface of the operating table (1) is fixedly connected to a fixing frame (8), and the upper surface of the fixing frame (8) is fixedly connected to the positioning table (9).

7. The high-precision positioning and vibration damping clamping fixture for a helicopter main gearbox housing according to claim 3, characterized in that, The first guide groove (303), the guide post (304), the moving stage (305), the first limiting component (5) and the second limiting component (6) are all provided in multiples and are distributed in a ring array.

8. The high-precision positioning and vibration damping clamping fixture for a helicopter main gearbox housing according to claim 3, characterized in that, The guide assembly (7) includes a slider (702), the upper surface of which is fixedly connected to the moving stage (305), and a second guide groove (703) is provided inside the slider (702).

9. A high-precision positioning and vibration damping clamping fixture for a helicopter main gearbox housing according to claim 8, characterized in that, The upper surface of the processing table (2) is fixedly connected to a guide block (701), and the inner surface of the second guide groove (703) is slidably connected to the guide block (701).

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